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Radiative Heating on the After-Body of Martian Entry Vehicles

机译：火星进入车辆后车身的辐射加热

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摘要

The radiative heat flux imparted on the after-body of vehicles entering the Martian atmosphere is simulated. The radiation is dominated by CO2 bands emitting in the midwave infrared. This mechanism traditionally has not been considered in the design of past Mars entry vehicles. However, with recent analysis showing that CO2 radiative heating can exceed convective heating on after-body surfaces, and with several upcoming and proposed missions to Mars potentially affected, an investigation of this radiation is warranted. This paper aims to quantify and improve understanding of the impact of radiation to aerothermal heating predictions for Mars entry. The tangent-slab approximation is shown to be overly conservative, by as much as 58%, for most of the backshell compared with using a full angular integration method. However, due to the complexity of the wake flow, it is also shown that tangent slab does not always represent an upper limit for radiative heating. Furthermore, analysis shows that it is not possible to provide a general correction factor to convert tangent-slab results to those obtained using the more rigorous full integration method. Radiative heating on the after-body often exceeds convective heating and therefore must be included in thermal protection system design for future missions.
机译：模拟了进入火星大气层的车辆后车身上的辐射热通量。辐射以中波红外发射的CO2波段为主。传统上，在过去的火星进入载具的设计中并未考虑这种机制。但是，最近的分析表明，CO2辐射加热可能超过车身后部表面的对流加热，并且由于即将进行和拟议的几次前往火星的任务都可能受到影响，因此有必要对此辐射进行调查。本文旨在量化和增进对辐射对火星进入的空气热加热预测的影响的理解。与使用全角积分方法相比，对于大多数后壳，切线-平板近似值显示的过于保守，高达58％。然而，由于尾流的复杂性，还表明切线板并不总是代表辐射加热的上限。此外，分析表明不可能提供一般的校正因子来将切线结果转换为使用更严格的完全积分方法获得的结果。车身后部的辐射加热通常超过对流加热，因此必须将其包括在热保护系统设计中，以备将来使用。

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  • 来源
    《Journal of Thermophysics and Heat Transfer》 |2020年第1期|66-77|共12页
  • 作者

    Brandis A. M.; Saunders D. A.; Johnston C. O.; Cruden B. A.; White T. R.;

  • 作者单位

    NASA Analyt Mech Associates Inc Ames Res Ctr Aerothermodynam Branch Moffett Field CA 94035 USA|AIAA Reston VA 20191 USA;

    NASA Langley Res Ctr Aerothermodynam Branch Hampton VA 23669 USA|AIAA Reston VA 20191 USA;

    NASA Ames Res Ctr Entry Syst & Vehicle Dev Branch Moffett Field CA 94035 USA|AIAA Reston VA 20191 USA;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);美国《生物学医学文摘》(MEDLINE);
  • 原文格式 PDF
  • 正文语种 eng
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